real gas effect, hypersonic flow, chemical equilibrium, shock tunnel, flow analysis system, multi block grid, wing body model, finite volume method, TVD upwind scheme, total variation diminishing, stagnation point, shock wave interaction, frozen flow, aerodynamic heating, Navier Stokes analysis system
その他のタイトル（英）
Validation of the computation of hypersonic flow with real gas effects
Kawasaki Heavy Industries Ltd Space Project Engineering Department
Kawasaki Heavy Industries Ltd Space Project Engineering Department
National Space Development Agency of Japan
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
34
ページ
67 - 72
発行年
1997-01
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 6-7 JUN. 1996 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 6-7 JUN. 1996 Tokyo Japan
The validation of the computation of hypersonic flow with real gas effects, that is assumed to be chemical equilibrium, have been carried out by the comparison with the HEG (High Enthalpy shock tunnel in Goettingen) shock tunnel test data. The flow analysis system uses a structured multi-block grid, and is based on finite volume TVD (Total Variation Diminishing) upwind scheme with the curve fitting to estimate chemical equilibrium real gas effects. Calculations were done to the flows around a sphere and the simple wing-body model respectively. The numerical results of the flow around a sphere showed very good agreement with the shock tunnel test data in the view of heat flux at a stagnation point. The results of the simple wing-body model were qualitatively improved by taking account of real gas effects with respect to the location and value of peak heat flux by shock-shock interaction, compared with frozen flow results.
実在気体効果をともなう極超音速流解析の検証
nalsp0034013.pdf
(621.26KB)
